EASA AD No.: 2015-0056

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0056

Date: 31 March 2015
Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EU 1321/2014 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se specified by the Agency [EU 1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, A rticle 14(4) exemption]. 

### Design Approval Holder’s Name: ROLLS-ROYCE DEUTSCHLAND Ltd & Co KG Type/Model designation(s): Tay 650 and Tay 651 engines

TCDS Number: EASA.E.063

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2007-0086 d ated 30 March 2007.



### ATA 72 Engine – High Pressure Turbine Stage 1 Disc – Cycli c Life Limit Reduction

Manufacturer(s): Rolls-Royce plc

Applicability: Tay 650-15 and Tay 651-54 engines, a ll variants, all serial numbers. These engines are known to be installed on, but not limited to, Fokker F28 Mark 0100 and Boeing 727 series aeroplanes.
Reason: A recent analysis identified the need to re duce the existing cyclic life limit of certain High Pressure Turbine (HPT) Stage 1 discs, Part Number (P/N) JR32013, as compared with the values published in R RD Tay 650 and Tay 651 engine Time Limit Manuals (TLM), Chapter 05-10-01. Operation of the affected HPT Stage 1 disc P/N JR32 013 beyond the reduced cyclic life limit would likely result in an unsafe condition. This condition, if not corrected, could lead to par t failure, possibly resulting in release of high energy debris with consequent damag e to the aeroplane and/or injury to the occupants. Prompted by the analysis results, RRD issued Alert Non Modification Service Bulletin (NMSB) TAY-72-A1821 to inform about the re duced cyclic life limits for various affected flight plans. For the reasons described above, this AD requires i mplementation of the reduced cyclic life limits, as applicable to the va rious flight plans and replacement of HPT Stage 1 disc P/N JR32013 that ha ve already exceeded the reduced cyclic life limit.EASA AD No.: 2015-0056

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Effective Date: 14 April 2015

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: For engines with a HPT Stage 1 disc P/N JR32013 ins talled, before exceeding the cyclic life limit as indicated in Table 1 of th is AD, depending on flight plan the engine is operated in, as applicable, or within 100 flight cycles (FC) after the effective date of this AD, whichever occurs later, replace the HPT disc P/N JR32013 with a serviceable part in accordance with the instructions of RRD NMSB TAY-72-A1821.

Table 1 HPT Stage 1 disc P/N JR32013 Life Limitatio n Engine Model Flight Plan Life Limit

Tay 650-15 A 18 900 FC
B 15 500 FC
C 11 500 FC
D 9 300 FC Tay 651-54 N/A 10 873 FC

Ref. Publications: RRD NMSB TAY-72-A1821 Revision 0 1 dated 26 March 2015.
The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 02 February 2015 as PAD 15 -008 for consultation until 02 March 2015. The Comment Response Document can be found at http://ad.easa.europa.eu

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: Rolls-Royce Deutschland Ltd & Co KG Eschenweg 11,D-15827 Blankenfelde-Mahlow, Germany Telephone: +49 (0) 33 7086 1768, Fax +49 (0) 33 708 6 3356 E-mail: RRDTechnicalHelpdesk@Rolls-Royce.com

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